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eliminating the possibility of residual fuel burning during the next start cycle. The flow of air through the holes and louvers of the can-annular chambers is the same as the flow through other types of burners. Figure 1-31 shows the flow of combustion air, metal-cooling air, and the diluent or gas- cooling air. Pay particular attention to the direction of airflow, indicated by the arrows. TURBINE SECTION The turbine transforms a portion of the kinetic (velocity) energy of the exhaust gases into mechanical energy to drive the compressor and necessary accessories. This is the sole purpose of the turbine. This function absorbs about 60 to 80 percent of the total pressure energy from the exhaust gases. The exact amount of energy absorption at the turbine is determined by the load the turbine is driving. The compressor size, type, accessories, and a propeller and its reduction gears if the engine is a turbo-propeller type, also affect absorption. The turbine section of a turbojet engine is located aft, or downstream, of the combustion chamber section. Specifically, it is directly behind the combustion chamber outlet. The turbine assembly consists of two basic elements, the stator and the rotor, as does the compressor unit. These two elements are shown in Figures 1-32 and 1- 33. The stator element is known by a variety of names. Turbine nozzle vanes, turbine inlet guide vanes, and nozzle diaphragm are three of the most commonly used. The turbine nozzle vanes are located directly aft of the combustion chambers and immediately forward of the turbine wheel. The function of the turbine nozzle is twofold. First, after the combustion chamber has introduced the heat energy into the mass airflow and delivered it evenly to the turbine nozzle, it becomes the job of the nozzle to prepare the mass flow for harnessing of power through the turbine rotor. The stationary vanes of the turbine nozzle are contoured and set at such an angle that they form small nozzles. They discharge the gas as extremely high-speed jets. Thus, the nozzle converts a varying portion of the heat and pressure energy to velocity energy. It can then be converted to mechanical energy through the rotor blades. The second purpose of the turbine nozzle is to deflect the gases to a specific angle in the direction of turbine wheel rotation. Since the gas flow from the nozzle must enter the turbine blade passageway while the turbine is still rotating, it is essential to aim the gas in the general direction of turbine rotation. The elements of the turbine nozzle assembly consist of an inner shroud and an outer shroud, between the nozzle vanes. The number of 1-23 Figure 1-32 — Stator element of the turbine assembly. Figure 1-33 — Rotor element of the turbine assembly.PDF Image | JET ENGINE THEORY AND DESIGN
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